CN111645882A - Satellite autonomous orbit determination method, device, equipment and computer storage medium - Google Patents
Satellite autonomous orbit determination method, device, equipment and computer storage medium Download PDFInfo
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Abstract
The embodiment of the invention provides a satellite autonomous orbit determination method, a satellite autonomous orbit determination device, satellite autonomous orbit determination equipment and a computer storage medium. The satellite autonomous orbit determination method based on the Beidou navigation system is applied to a target satellite and comprises the following steps: determining first position information of a target satellite based on a Miniature Inertial Measurement Unit (MIMU) in the target satellite; receiving first differential data corresponding to first position information sent by a Beidou navigation system based on a satellite-borne Beidou receiver in a target satellite; the first differential data is determined by the Beidou navigation system according to the first position information and a preset mapping relation, and the mapping relation is the mapping relation between the position information and the differential data; resolving the first position information by using the first differential data to obtain second position information; and determining the satellite orbit of the target satellite based on the second position information. According to the satellite autonomous orbit determination method, the satellite autonomous orbit determination device, the satellite autonomous orbit determination equipment and the computer storage medium, satellite autonomous orbit determination can be performed more accurately.
Description
Technical Field
The invention belongs to the technical field of satellite autonomous orbit determination, and particularly relates to a satellite autonomous orbit determination method, a satellite autonomous orbit determination device, satellite autonomous orbit determination equipment and a computer storage medium based on a Beidou navigation system.
Background
The autonomous orbit determination of the satellite refers to the autonomous determination of the satellite orbit of the satellite under the condition of not depending on the measurement and control of ground personnel. Before determining the satellite orbit to which the satellite belongs, the position information of the satellite needs to be determined.
Currently, in the related art, the position information of the satellite is determined by transmitting a signal to a ground center, and the ground center then determines the position information of the satellite based on the signal. However, in the process of transmitting signals, the signals are affected by error sources such as an ionosphere and a troposphere, so that the position information of the satellite is determined inaccurately, and the autonomous orbit determination of the satellite is inaccurate.
Therefore, how to more accurately perform autonomous satellite orbit determination is a technical problem that needs to be solved urgently by those skilled in the art.
Disclosure of Invention
The embodiment of the invention provides a satellite autonomous orbit determination method, a satellite autonomous orbit determination device, satellite autonomous orbit determination equipment and a computer storage medium based on a Beidou navigation system, and satellite autonomous orbit determination can be performed more accurately.
In a first aspect, an embodiment of the present invention provides a satellite autonomous orbit determination method based on a beidou navigation system, which is applied to a target satellite, and includes:
determining first position information of a target satellite based on a Miniature Inertial Measurement Unit (MIMU) in the target satellite;
receiving first differential data corresponding to first position information sent by a Beidou navigation system based on a satellite-borne Beidou receiver in a target satellite; the first differential data is determined by the Beidou navigation system according to the first position information and a preset mapping relation, and the mapping relation is the mapping relation between the position information and the differential data;
resolving the first position information by using the first differential data to obtain second position information;
and determining the satellite orbit of the target satellite based on the second position information.
Optionally, after determining the satellite orbit to which the target satellite belongs based on the second position information, the method further includes:
and determining the orbit change information for changing the satellite orbit of the target satellite based on the GNC system and the orbital transfer algorithm of the target satellite, so as to control and change the satellite orbit of the target satellite according to the orbit change information.
Optionally, when the orbital transfer algorithm is a space intersection phase modulation special point orbital transfer solving algorithm, determining, based on the GNC system of the target satellite and the orbital transfer algorithm, orbital change information for changing the satellite orbit to which the target satellite belongs, so as to control to change the satellite orbit to which the target satellite belongs according to the orbital change information, including:
the method comprises the steps of determining orbit change information for changing the satellite orbit of a target satellite based on a GNC system of the target satellite and a space rendezvous phase modulation special point orbital transfer solving algorithm, and controlling a power device in the target satellite to start according to the orbit change information to change the satellite orbit of the target satellite.
Optionally, the method further comprises:
determining the flight attitude and the flight speed of the target satellite based on the MIMU;
and controlling a power device in the target satellite to start based on the GNC system and the orbital transfer algorithm of the target satellite so as to change the flight attitude and the flight speed of the target satellite.
In a second aspect, an embodiment of the present invention provides a satellite autonomous orbit determination apparatus based on a beidou navigation system, which is applied to a target satellite, and includes:
the first determining module is used for determining first position information of the target satellite based on a Miniature Inertial Measurement Unit (MIMU) in the target satellite;
the receiving module is used for receiving first differential data corresponding to first position information sent by a Beidou navigation system based on a satellite-borne Beidou receiver in a target satellite; the first differential data is determined by the Beidou navigation system according to the first position information and a preset mapping relation, and the mapping relation is the mapping relation between the position information and the differential data;
the resolving module is used for resolving the first position information by utilizing the first differential data to obtain second position information;
and the second determining module is used for determining the satellite orbit of the target satellite based on the second position information.
Optionally, the apparatus further comprises:
and the first orbital transfer module is used for determining the orbit change information for changing the satellite orbit of the target satellite based on the GNC system and the orbital transfer algorithm of the target satellite, and is used for controlling and changing the satellite orbit of the target satellite according to the orbit change information.
Optionally, when the orbital transfer algorithm is a space intersection phase modulation special point orbital transfer solving algorithm, the first orbital transfer module is configured to determine, based on the GNC system of the target satellite and the space intersection phase modulation special point orbital transfer solving algorithm, orbit change information for changing the satellite orbit of the target satellite, and be configured to control a power device in the target satellite to start according to the orbit change information to change the satellite orbit of the target satellite.
Optionally, the apparatus further comprises:
the third determining module is used for determining the flight attitude and the flight speed of the target satellite based on the MIMU;
and the second orbital transfer module is used for controlling the starting of a power device in the target satellite based on the GNC system and the orbital transfer algorithm of the target satellite so as to change the flight attitude and the flight speed of the target satellite.
In a third aspect, an embodiment of the present invention provides an electronic device, where the device includes: a processor, and a memory storing computer program instructions;
the processor reads and executes the computer program instructions to implement the autonomous satellite orbit determination method based on the beidou navigation system in the first aspect or any optional implementation manner of the first aspect.
In a fourth aspect, an embodiment of the present invention provides a computer storage medium, where computer program instructions are stored on the computer storage medium, and when the computer program instructions are executed by a processor, the method for autonomous satellite orbit determination based on a beidou navigation system in the first aspect or any optional implementation manner of the first aspect is implemented.
The satellite autonomous orbit determination method, the satellite autonomous orbit determination device, the satellite autonomous orbit determination equipment and the computer storage medium based on the Beidou navigation system can more accurately perform satellite autonomous orbit determination. The satellite autonomous orbit determination method based on the Beidou navigation system comprises the steps of firstly determining first position information of a target satellite based on an MIMU (micro inertial measurement Unit) in the target satellite; then, receiving first differential data corresponding to first position information sent by a Beidou navigation system based on a satellite-borne Beidou receiver in a target satellite; the first position information is resolved by utilizing the first differential data, namely the first position information is corrected, so that the influence of error sources such as an ionized layer and a troposphere in the related technology can be counteracted, more accurate second position information can be obtained, and further, the satellite orbit to which the target satellite belongs can be more accurately determined based on the second position information, namely, the satellite autonomous orbit determination can be more accurately carried out.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the embodiments of the present invention will be briefly described below, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic flow chart of a satellite autonomous orbit determination method based on a Beidou navigation system, provided by an embodiment of the invention;
fig. 2 is a schematic structural diagram of a satellite autonomous orbit determination device based on a beidou navigation system according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of an electronic device according to an embodiment of the present invention.
Detailed Description
Features and exemplary embodiments of various aspects of the present invention will be described in detail below, and in order to make objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention. It will be apparent to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
Currently, in the related art, the position information of the satellite is determined by transmitting a signal to a ground center, and the ground center then determines the position information of the satellite based on the signal. However, in the process of transmitting signals, the signals are affected by error sources such as an ionosphere and a troposphere, so that the position information of the satellite is determined inaccurately, and the autonomous orbit determination of the satellite is inaccurate.
In order to solve the problems in the prior art, the embodiment of the invention provides a satellite autonomous orbit determination method, a satellite autonomous orbit determination device, satellite autonomous orbit determination equipment and a computer storage medium based on a Beidou navigation system. First, a satellite autonomous orbit determination method based on a Beidou navigation system provided by the embodiment of the invention is introduced below.
Fig. 1 shows a schematic flow diagram of a satellite autonomous orbit determination method based on a Beidou navigation system, which is provided by the embodiment of the invention. As shown in fig. 1, the autonomous satellite orbit determination method based on the beidou navigation system may include the following steps:
s101, determining first position information of the target satellite based on the MIMU in the target satellite.
S102, receiving first differential data corresponding to first position information sent by a Beidou navigation system based on a satellite-borne Beidou receiver in a target satellite; the first differential data is determined by the Beidou navigation system according to the first position information and a preset mapping relation, and the mapping relation is the mapping relation between the position information and the differential data.
S103, resolving the first position information by using the first difference data to obtain second position information.
And S104, determining the satellite orbit of the target satellite based on the second position information.
The satellite autonomous orbit determination method based on the Beidou navigation system is applied to a target satellite, and first position information of the target satellite is determined based on an MIMU in the target satellite; then, receiving first differential data corresponding to first position information sent by a Beidou navigation system based on a satellite-borne Beidou receiver in a target satellite; the first position information is resolved by utilizing the first differential data, namely the first position information is corrected, so that the influence of error sources such as an ionized layer and a troposphere in the related technology can be counteracted, more accurate second position information can be obtained, and further, the satellite orbit to which the target satellite belongs can be more accurately determined based on the second position information, namely, the satellite autonomous orbit determination can be more accurately carried out.
To implement autonomous orbital transfer of the target satellite, in one embodiment, after determining the satellite orbit to which the target satellite belongs based on the second location information, the method may further include:
and determining the orbit change information for changing the satellite orbit of the target satellite based on the GNC system and the orbital transfer algorithm of the target satellite, so as to control and change the satellite orbit of the target satellite according to the orbit change information. Optionally, the orbital transfer algorithm is a high-precision orbital transfer algorithm.
In order to enable the target satellite to perform autonomous orbital transfer more accurately, in one embodiment, when the orbital transfer algorithm is a space intersection phase modulation special point orbital transfer solution algorithm, determining, based on the GNC system and the orbital transfer algorithm of the target satellite, orbital change information for changing the satellite orbit to which the target satellite belongs, so as to control to change the satellite orbit to which the target satellite belongs according to the orbital change information, may include: the method comprises the steps of determining orbit change information for changing the satellite orbit of a target satellite based on a GNC system of the target satellite and a space rendezvous phase modulation special point orbital transfer solving algorithm, and controlling a power device in the target satellite to start according to the orbit change information to change the satellite orbit of the target satellite.
To achieve autonomous attitude change of the target satellite, in one embodiment, the method may further comprise: determining the flight attitude and the flight speed of the target satellite based on the MIMU; and controlling a power device in the target satellite to start based on the GNC system and the orbital transfer algorithm of the target satellite so as to change the flight attitude and the flight speed of the target satellite.
Fig. 2 is a schematic structural diagram of a satellite autonomous orbit determination device based on a Beidou navigation system, provided by the embodiment of the invention. As shown in FIG. 2, the autonomous satellite orbit determination device based on the Beidou navigation system is applied to a target satellite and can comprise
A first determining module 201, configured to determine first position information of a target satellite based on a micro inertial measurement unit MIMU in the target satellite;
the receiving module 202 is used for receiving first differential data corresponding to first position information sent by a Beidou navigation system based on a satellite-borne Beidou receiver in a target satellite; the first differential data is determined by the Beidou navigation system according to the first position information and a preset mapping relation, and the mapping relation is the mapping relation between the position information and the differential data;
the calculating module 203 is configured to calculate the first position information by using the first differential data to obtain second position information;
and a second determining module 204, configured to determine, based on the second position information, a satellite orbit to which the target satellite belongs.
Optionally, in an embodiment, the apparatus may further include:
and the first orbital transfer module is used for determining the orbit change information for changing the satellite orbit of the target satellite based on the GNC system and the orbital transfer algorithm of the target satellite, and is used for controlling and changing the satellite orbit of the target satellite according to the orbit change information.
Optionally, in an embodiment, when the orbital transfer algorithm is a space rendezvous phase modulation special point orbital transfer solution algorithm, the first orbital transfer module is configured to determine, based on the GNC system of the target satellite and the space rendezvous phase modulation special point orbital transfer solution algorithm, orbital change information for changing an orbit of a satellite to which the target satellite belongs, and to control a power device in the target satellite to start according to the orbital change information to change the orbit of the satellite to which the target satellite belongs.
Optionally, in an embodiment, the apparatus may further include:
the third determining module is used for determining the flight attitude and the flight speed of the target satellite based on the MIMU;
and the second orbital transfer module is used for controlling the starting of a power device in the target satellite based on the GNC system and the orbital transfer algorithm of the target satellite so as to change the flight attitude and the flight speed of the target satellite.
Each module in the apparatus shown in fig. 2 has a function of implementing each step executed by the target satellite in fig. 1, and can achieve the corresponding technical effect, and for brevity, no further description is given here.
Fig. 3 shows a schematic structural diagram of an electronic device according to an embodiment of the present invention.
The electronic device may comprise a processor 301 and a memory 302 in which computer program instructions are stored.
Specifically, the processor 301 may include a Central Processing Unit (CPU), an Application Specific Integrated Circuit (ASIC), or one or more Integrated circuits configured to implement the embodiments of the present invention.
In one example, the Memory 302 may be a Read Only Memory (ROM). In one example, the ROM may be mask programmed ROM, programmable ROM (prom), erasable prom (eprom), electrically erasable prom (eeprom), electrically rewritable ROM (earom), or flash memory, or a combination of two or more of these.
The processor 301 reads and executes the computer program instructions stored in the memory 302 to implement the method in the embodiment shown in fig. 1, and achieves the corresponding technical effect achieved by the embodiment shown in fig. 1 executing the method, which is not described herein again for brevity.
In one example, the electronic device may also include a communication interface 303 and a bus 310. As shown in fig. 3, the processor 301, the memory 302, and the communication interface 303 are connected via a bus 310 to complete communication therebetween.
The communication interface 303 is mainly used for implementing communication between modules, apparatuses, units and/or devices in the embodiment of the present invention.
In addition, embodiments of the present invention may be implemented by providing a computer storage medium. The computer storage medium having computer program instructions stored thereon; the computer program instructions, when executed by the processor, implement the autonomous satellite orbit determination method based on the beidou navigation system shown in fig. 1.
It is to be understood that the invention is not limited to the specific arrangements and instrumentality described above and shown in the drawings. A detailed description of known methods is omitted herein for the sake of brevity. In the above embodiments, several specific steps are described and shown as examples. However, the method processes of the present invention are not limited to the specific steps described and illustrated, and those skilled in the art can make various changes, modifications and additions or change the order between the steps after comprehending the spirit of the present invention.
The functional blocks shown in the above-described structural block diagrams may be implemented as hardware, software, firmware, or a combination thereof. When implemented in hardware, it may be, for example, an electronic Circuit, an Application Specific Integrated Circuit (ASIC), suitable firmware, plug-in, function card, or the like. When implemented in software, the elements of the invention are the programs or code segments used to perform the required tasks. The program or code segments may be stored in a machine-readable medium or transmitted by a data signal carried in a carrier wave over a transmission medium or a communication link. A "machine-readable medium" may include any medium that can store or transfer information. Examples of a machine-readable medium include electronic circuits, semiconductor memory devices, ROM, flash memory, Erasable ROM (EROM), floppy disks, CD-ROMs, optical disks, hard disks, fiber optic media, Radio Frequency (RF) links, and so forth. The code segments may be downloaded via computer networks such as the internet, intranet, etc.
It should also be noted that the exemplary embodiments mentioned in this patent describe some methods or systems based on a series of steps or devices. However, the present invention is not limited to the order of the above-described steps, that is, the steps may be performed in the order mentioned in the embodiments, may be performed in an order different from the order in the embodiments, or may be performed simultaneously.
As described above, only the specific embodiments of the present invention are provided, and it can be clearly understood by those skilled in the art that, for convenience and brevity of description, the specific working processes of the system, the module and the unit described above may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again. It should be understood that the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.
Claims (10)
1. A satellite autonomous orbit determination method based on a Beidou navigation system is characterized by being applied to a target satellite and comprising the following steps:
determining first position information of the target satellite based on a Miniature Inertial Measurement Unit (MIMU) in the target satellite;
receiving first differential data corresponding to the first position information sent by a Beidou navigation system based on a satellite-borne Beidou receiver in the target satellite; the first differential data is determined by the Beidou navigation system according to the first position information and a preset mapping relation, and the mapping relation is between the position information and the differential data;
resolving the first position information by using the first differential data to obtain second position information;
and determining the satellite orbit of the target satellite based on the second position information.
2. The autonomous satellite orbit determination method based on the beidou navigation system of claim 1, wherein after determining the satellite orbit to which the target satellite belongs based on the second position information, the method further comprises:
and determining the orbit change information for changing the satellite orbit of the target satellite based on the GNC system and the orbital transfer algorithm of the target satellite, so as to control to change the satellite orbit of the target satellite according to the orbit change information.
3. The autonomous satellite orbit determination method based on the beidou navigation system of claim 2, wherein when the orbital transfer algorithm is a space intersection phase modulation special point orbital transfer solution algorithm, the GNC system and the orbital transfer algorithm based on the target satellite determine orbit change information for changing the satellite orbit to which the target satellite belongs, so as to control to change the satellite orbit to which the target satellite belongs according to the orbit change information, and the method comprises the following steps:
and determining orbit change information for changing the satellite orbit of the target satellite based on the GNC system of the target satellite and the special point orbital transfer solution algorithm for space intersection phase modulation, so as to control a power device in the target satellite to start according to the orbit change information and change the satellite orbit of the target satellite.
4. The autonomous satellite orbit determination method based on the Beidou navigation system, according to claim 1, is characterized in that the method further comprises:
determining the flight attitude and the flight speed of the target satellite based on the MIMU;
controlling a power device in the target satellite to start based on the GNC system and the orbital transfer algorithm of the target satellite so as to change the flying attitude and the flying speed of the target satellite.
5. The utility model provides a satellite is orbit determination device independently based on beidou navigation system which characterized in that is applied to the target satellite, includes:
the first determining module is used for determining first position information of the target satellite based on a Miniature Inertial Measurement Unit (MIMU) in the target satellite;
the receiving module is used for receiving first differential data corresponding to the first position information sent by the Beidou navigation system based on a satellite-borne Beidou receiver in the target satellite; the first differential data is determined by the Beidou navigation system according to the first position information and a preset mapping relation, and the mapping relation is between the position information and the differential data;
the calculating module is used for calculating the first position information by using the first differential data to obtain second position information;
and the second determining module is used for determining the satellite orbit of the target satellite based on the second position information.
6. The Beidou navigation system based satellite autonomous orbit determination device of claim 5, further comprising:
and the first orbital transfer module is used for determining the orbit change information for changing the satellite orbit of the target satellite based on the GNC system and the orbital transfer algorithm of the target satellite, and is used for controlling the change of the satellite orbit of the target satellite according to the orbit change information.
7. The autonomous satellite orbit determination device based on the beidou navigation system of claim 6, wherein when the orbital transfer algorithm is a special point orbital transfer solution algorithm for space intersection phase modulation, the first orbital transfer module is configured to determine, based on the GNC system of the target satellite and the special point orbital transfer solution algorithm for space intersection phase modulation, orbit change information for changing the satellite orbit of the target satellite, so as to control a power device in the target satellite to start according to the orbit change information, and change the satellite orbit of the target satellite.
8. The Beidou navigation system based satellite autonomous orbit determination device of claim 5, further comprising:
the third determining module is used for determining the flight attitude and the flight speed of the target satellite based on the MIMU;
and the second orbital transfer module is used for controlling a power device in the target satellite to start so as to change the flying attitude and the flying speed of the target satellite based on the GNC system and the orbital transfer algorithm of the target satellite.
9. An electronic device, characterized in that the device comprises: a processor, and a memory storing computer program instructions;
the processor reads and executes the computer program instructions to realize the autonomous satellite orbit determination method based on the Beidou navigation system according to any one of claims 1 to 4.
10. A computer storage medium having computer program instructions stored thereon, which when executed by a processor, implement the autonomous satellite orbit determination method according to any one of claims 1 to 4.
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